Federal Register / Vol. 72, No. 70 / Thursday, April 12, 2007 / Rules and Regulations 18375 

the end of the 20 second period 

specified in § 25.335(b)(1)—the 

following special condition applies. 

The greater of the speeds resulting 

from the conditions of paragraphs (a) 

and (b), below, must be used. 

(a) From an initial condition of 

stabilized flight at VC/MC, the airplane 

is upset so as to take up a new flight 

path 7.5 degrees below the initial path. 

Control application, up to full authority, 

is made to try and maintain this new 

flight path. Twenty seconds after 

initiating the upset, manual recovery is 

made at a load factor of 1.5 g (0.5 

acceleration increment) or such greater 

load factor that is automatically applied 

by the system with the pilot’s pitch 

control neutral. The speed increase 

occurring in this maneuver may be 

calculated, if reliable or conservative 

aerodynamic data is used. Power, as 

specified in § 25.175(b)(1)(iv), is 

assumed until recovery is made, at 

which time power reduction and the use 

of pilot controlled drag devices may be 

used. 

(b) From a speed below VC/MC with 

power to maintain stabilized level flight 

at this speed, the airplane is upset so as 

to accelerate through VC/MC at a flight 

path 15 degrees below the initial path—

or at the steepest nose down attitude 

that the system will permit with full 

control authority if less than 15 degrees. 

Note: The pilot’s controls may be in the 

neutral position after reaching VC/MC and 

before recovery is initiated. 

(c) Recovery may be initiated three 

seconds after operation of high speed 

warning system by application of a load 

of 1.5 g (0.5 acceleration increment) or 

such greater load factor that is 

automatically applied by the system 

with the pilot’s pitch control neutral. 

Power may be reduced simultaneously. 

All other means of decelerating the 

airplane, the use of which is authorized 

up to the highest speed reached in the 

maneuver, may be used. The interval 

between successive pilot actions must 

not be less than one second. 

(d) The applicant must also 

demonstrate that the design dive speed, 

established above, will not be exceeded 

during pilot-induced or gust-induced 

upsets in non-symmetric attitudes. 

(e) The occurrence of any failure 

condition that would reduce the 

capability of the overspeed protection 

system must be improbable (less than 

10¥5 per flight hour). 

Issued in Renton, Washington, on April 4, 

2007. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E7–6889 Filed 4–11–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27552; Directorate 

Identifier 2007–NE–11–AD; Amendment 39–

15019; AD 2007–08–02] 

RIN 2120–AA64 

Airworthiness Directives; Hartzell 

Propeller Inc. Model HC–E4A–3( )/ 

E10950( ) Propellers 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for Hartzell 

Propeller Inc. model HC–E4A–3( )/ 

E10950( ) propellers. This AD requires 

initial and repetitive inspections and 

rework of the propeller blade retention 

radius, and replacement of the propeller 

blade thrust bearing, for each blade. 

This AD results from reports of 

excessive propeller vibration and of 

damaged or broken propeller blade 

thrust bearings found during routine 

and investigative propeller disassembly. 

We are issuing this AD to prevent 

propeller blade separation, damage to 

the airplane, and possible loss of 

airplane control. 

DATES: This AD becomes effective April 

27, 2007. The Director of the Federal 

Register approved the incorporation by 

reference of certain publications listed 

in the regulations as of April 27, 2007. 

We must receive any comments on 

this AD by June 11, 2007. 

ADDRESSES: Use one of the following 

addresses to comment on this AD: 

• DOT Docket Web site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Government-wide rulemaking Web 

site: Go to http://www.regulations.gov 

and follow the instructions for sending 

your comments electronically. 

• Mail: Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590–

0001. 

• Fax: (202) 493–2251. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street, SW., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

Contact Hartzell Propeller Inc. 

Technical Publications Department, One 

Propeller Place, Piqua, OH 45356; 

telephone (937) 778–4200; fax (937) 

778–4391, for the service information 

identified in this AD. 

FOR FURTHER INFORMATION CONTACT: Tim 

Smyth, Aerospace Engineer, Chicago 

Aircraft Certification Office, FAA, Small 

Airplane Directorate, 2300 East Devon 

Avenue, Des Plaines, IL 60018; e-mail: 

tim.smyth@faa.gov; telephone: (847) 

294–7132; fax: (847) 294–7834. 

SUPPLEMENTARY INFORMATION: We have 

received reports of excessive propeller 

vibration, and of damaged or broken 

propeller blade thrust bearings on 

Hartzell Propeller Inc. model HC–E4A–

3( )/E10950( ) propellers found during 

routine and investigative propeller 

disassembly. At least 15 propellers have 

been reported with broken propeller 

blade thrust bearings. During teardowns, 

instances of bearing failures have been 

progressively more severe, with more 

internal damage to the hub noted. 

Service history shows the propellers can 

safely accumulate 2,000 operating hours 

time-since-overhaul (TSO) before the 

unsafe conditions start to appear. A 

broken thrust bearing can lead to 

damage to the propeller hub and blade 

shank, and blade separation from the 

hub. These damaged or broken parts can 

also lead to damage to the internal 

propeller pitch change mechanism, 

resulting in loss of propeller pitch 

control or in difficulty in feathering the 

propeller. This condition, if not 

corrected, could result in propeller 

blade separation, damage to the 

airplane, and possible loss of airplane 

control. Repairing the propeller blade 

retention radius using the instructions 

cited in Hartzell Propeller Inc. Service 

Bulletin (SB) No. HC–SB–61–287, 

Revision 2, dated October 24, 2006, 

allows the propeller to safely operate for 

3,000 hours before requiring bearing 

replacement. 

Relevant Service Information 

We reviewed and approved the 

technical contents of Hartzell Propeller 

Inc. SB No. HC–SB–61–287, Revision 2, 

dated October 24, 2006. That SB 

describes procedures for initial and 

repetitive propeller blade inspection, 

rework, and thrust bearing replacement, 

for each blade. 


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18376 Federal Register / Vol. 72, No. 70 / Thursday, April 12, 2007 / Rules and Regulations 

Differences Between This AD and the 

Service Information 

Hartzell Propeller Inc. SB No. HC–

SB–61–287, Revision 2, dated October 

24, 2006, states in paragraph 3.G.(6) of 

the Accomplishment Instructions, to 

install new blade thrust bearings if 

required. However, this AD removes the 

option of ‘‘if required,’’ and mandates 

that operators must always install new 

blade thrust bearings. 

FAA’s Determination and Requirements 

of this AD 

The unsafe condition described 

previously is likely to exist or develop 

on other Hartzell Propeller Inc. model 

HC–E4A–3( )/E10950( ) propellers of 

the same type design. For that reason, 

we are issuing this AD to prevent 

propeller blade separation, damage to 

the airplane, and possible loss of 

airplane control. You must use the 

service information described 

previously to perform the actions 

required by this AD. 

This AD requires: 

• For propellers with 4,000 or more 

operating hours TSO, initial inspection 

and rework of the propeller blade 

retention radius and replacement of the 

propeller thrust bearing for each blade, 

within 100 operating hours after the 

effective date of the AD; and 

• For propellers with 2,000 or more 

operating hours TSO, but fewer than 

4,000 operating hours TSO, inspection 

and rework of the propeller blade 

retention radius and replacement of the 

propeller thrust bearing, for each blade, 

at the next propeller disassembly; and 

• Thereafter, after every 3,000 

additional operating hours time-inservice, inspection and rework of the 

propeller blade retention radius and 

replacement of the propeller blade 

thrust bearing, for each blade. 

You must use the service information 

described previously to perform the 

actions required by this AD. 

FAA’s Determination of the Effective 

Date 

Since an unsafe condition exists that 

requires the immediate adoption of this 

AD, we have found that notice and 

opportunity for public comment before 

issuing this AD are impracticable, and 

that good cause exists for making this 

amendment effective in less than 30 

days. 

Interim Action 

These actions are interim actions and 

we may take further rulemaking actions 

in the future. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety and 

was not preceded by notice and an 

opportunity for public comment; 

however, we invite you to send us any 

written relevant data, views, or 

arguments regarding this AD. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘AD Docket No. 

FAA–2007–27552; Directorate Identifier 

2007–NE–11–AD’’ in the subject line of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the rule that might suggest a 

need to modify it. 

We will post all comments we 

receive, without change, to http:// 

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this AD. Using the 

search function of the Docket 

Management System (DMS) Web site, 

anyone can find and read the comments 

in any of our dockets, including the 

name of the individual who sent the 

comment (or signed the comment on 

behalf of an association, business, labor 

union, etc). You may review the DOT’s 

complete Privacy Act Statement in the 

Federal Register published on April 11, 

2000 (65 FR 19477–78) or you may visit 

http://dms.dot.gov. 

Examining the AD Docket 

You may examine the docket that 

contains the AD, any comments 

received, and any final disposition in 

person at the Docket Management 

Facility between 9 a.m. and 5 p.m., 

Monday through Friday, except Federal 

holidays. The Docket Management 

Facility (telephone (800) 647–5227) is 

located on the plaza level of the 

Department of Transportation Nassif 

Building at the street address stated in 

ADDRESSES. Comments will be available 

in the AD docket shortly after the DMS 

receives them. 

Authority for this Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national Government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

3. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a summary of the costs 

to comply with this AD and placed it in 

the AD Docket. You may get a copy of 

this summary at the address listed 

under ADDRESSES. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Under the authority delegated to me 

by the Administrator, the Federal 

Aviation Administration amends part 39 

of the Federal Aviation Regulations (14 

CFR part 39) as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive: 

2007–08–02 Hartzell Propeller Inc.: 

Amendment 39–15019; Docket No. 

FAA–2007–27552; Directorate Identifier 

2007–NE–11–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective April 27, 2007. 


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Federal Register / Vol. 72, No. 70 / Thursday, April 12, 2007 / Rules and Regulations 18377 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Hartzell Propeller 

Inc. model HC–E4A–3( )/E10950( ) 

propellers. These propellers are installed on, 

but not limited to, Raytheon Beechcraft 

1900D airplanes. 

(d) The parentheses appearing in the 

propeller model number indicates the 

presence or absence of an additional letter(s) 

that varies the basic propeller model. This 

AD still applies regardless of whether these 

letters are present or absent in the propeller 

model designation. 

Unsafe Condition 

(e) This AD results from reports of 

excessive propeller vibration and of damaged 

or broken propeller blade thrust bearings 

found during routine and investigative 

propeller disassembly. We are issuing this 

AD to prevent propeller blade separation, 

damage to the airplane, and possible loss of 

airplane control. 

Interim Action 

(f) These actions are interim actions and 

we may take further rulemaking actions in 

the future. 

Compliance 

(g) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified unless the 

actions have already been done. 

Initial Inspection, Rework, and Replacement 

(h) For propellers with 4,000 or more 

operating hours time-since-overhaul (TSO, 

initially inspect and rework the propeller 

blade retention radius and replace the 

propeller thrust bearing for each blade, 

within 100 operating hours. 

(i) For propellers with 2,000 or more 

operating hours TSO, but fewer than 4,000 

operating hours TSO, inspect and rework the 

propeller blade retention radius and replace 

the propeller thrust bearing, for each blade, 

at the next propeller disassembly. 

(j) Use paragraphs 3.G.(1) through 3.G.(8) of 

the Accomplishment Instructions of Hartzell 

Propeller Inc. Service Bulletin No. HC–SB–

61–287, Revision 2, dated October 24, 2006, 

to do the actions in paragraphs (h) and (i) of 

this AD. 

(k) Although Hartzell Propeller Inc. SB No. 

HC–SB–61–287, Revision 2, dated October 

24, 2006, states in paragraph 3.G.(6) of the 

Accomplishment Instructions, to install new 

blade thrust bearings if required, this AD 

requires always installing new blade thrust 

bearings. 

Repetitive Inspection, Rework, and 

Replacement 

(l) Thereafter, after every 3,000 additional 

operating hours time-in-service, inspect and 

rework the propeller blade retention radius 

and replace the propeller blade thrust 

bearing, for each blade. 

(m) Use paragraphs 3.G.(1) through 3.G.(8) 

of the Accomplishment Instructions of 

Hartzell Propeller Inc. SB No. HC–SB–61–

287, Revision 2, dated October 24, 2006, to 

do these actions. 

(n) Although paragraph 3.G.(6) of the 

Accomplishment Instructions of Hartzell 

Propeller Inc. SB No. HC–SB–61–287, 

Revision 2, dated October 24, 2006, states to 

install new blade thrust bearings if required, 

this AD requires always installing new blade 

thrust bearings. 

Definition 

(o) For the purpose of this AD, next 

propeller disassembly is defined as any 

maintenance requiring separating of the 

propeller hub halves. 

Previous Credit 

(p) Previous credit is allowed for 

inspections, rework, and replacements that 

were done using the Original or Revision 1 

of Hartzell Propeller Inc. SB No. HC–SB–61–

287, before the effective date of this AD. 

Alternative Methods of Compliance 

(q) The Manager, Chicago Aircraft 

Certification Office, has the authority to 

approve alternative methods of compliance 

for this AD if requested using the procedures 

found in 14 CFR 39.19. 

Related Information 

(r) Contact Tim Smyth, Aerospace 

Engineer, Chicago Aircraft Certification 

Office, FAA, Small Airplane Directorate, 

2300 East Devon Avenue, Des Plaines, IL 

60018; e-mail: tim.smyth@faa.gov; telephone: 

(847) 294–7132; fax: (847) 294–7834, for 

more information about this AD. 

Material Incorporated by Reference 

(s) You must use the Hartzell Propeller Inc. 

service information specified in Table 1 of 

this AD to perform the checks required by 

this AD. The Director of the Federal Register 

approved the incorporation by reference of 

the documents listed in Table 1 of this AD 

in accordance with 5 U.S.C. 552(a) and 1 CFR 

part 51. Contact Hartzell Propeller Inc. 

Technical Publications Department, One 

Propeller Place, Piqua, OH 45356; telephone 

(937) 778–4200; fax (937) 778–4391, for a 

copy of this service information. You may 

review copies at the FAA, New England 

Region, Office of the Regional Counsel, 12 

New England Executive Park, Burlington, 

MA; or at the National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

TABLE 1.—INCORPORATION BY REFERENCE

Hartzell Propeller Inc. Service Bulletin No. Page Revision Date 

HC–SB–61–287, Total Pages: 32 ............................... ALL .............................................................................. 2 October 24, 2006. 

Appendix to HC–SB–61–287, Total Pages: 2 ............ ALL .............................................................................. 2 October 24, 2006. 

Issued in Burlington, Massachusetts, on 

April 3, 2007. 

Peter A. White, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E7–6586 Filed 4–11–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22898; Directorate 

Identifier 2005–NE–10–AD; Amendment 39–

15021; AD 2007–08–04] 

RIN 2120–AA64 

Airworthiness Directives; McCauley 

Propeller Systems Models 3A32C406/ 

82NDB–X and D3A32C409/82NDB–X 

Propellers 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for 

McCauley Propeller Systems models 

3A32C406/82NDB–X and D3A32C409/ 

82NDB–X propellers, installed on 

Teledyne Continental Motors (TCM) IO–

520, TSIO–520, or IO–550 reciprocating 

engines. These propellers are herein 

referred to as C406 and C409 propellers, 

respectively. This AD requires adding 

an operational revolutions per minute 

(RPM) restriction on the C406 and C409 

propellers, and installing an RPM 

restriction placard in the cockpit. This 

AD also adds a 10,000-hour total timein-service (TIS) life limit for these 

propellers. This AD also removes from 


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